U.S. patent number 10,370,120 [Application Number 15/486,481] was granted by the patent office on 2019-08-06 for launcher for an unmanned aircraft and methods of use thereof.
This patent grant is currently assigned to The Government of the United States of America as Represented by the Secretary of the Navy. The grantee listed for this patent is The United States of America as Represented by the Secretary of the Navy. Invention is credited to Nicholas McGaha, Shawn Kerry McGann, Alvin L. Quintana.
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United States Patent |
10,370,120 |
McGann , et al. |
August 6, 2019 |
Launcher for an unmanned aircraft and methods of use thereof
Abstract
A launcher for an unmanned aircraft may comprise: a launch rail,
a carriage, pair of pulley drivers, and a cable and pulley system.
The pulley drivers may produce opposing pulley drive forces, which
may be converted into a single launching force via the cable and
pulley system for launching the carriage. The cable and pulley
system may comprise: launch rail pulleys, pulley block pulleys, cam
pulleys, drive cables, and one or more winches. Embodiments of the
launcher may apply a constant force to the aircraft uniformly over
the launch distance, such that the unmanned aircraft may be
propelled within a relatively short distance by applying energy to
the aircraft in the smallest period of time and without exceeding
the aircraft's acceleration limits.
Inventors: |
McGann; Shawn Kerry
(Ridgecrest, CA), McGaha; Nicholas (Ridgecrest, CA),
Quintana; Alvin L. (Ridgecrest, CA) |
Applicant: |
Name |
City |
State |
Country |
Type |
The United States of America as Represented by the Secretary of the
Navy |
Washington |
DC |
US |
|
|
Assignee: |
The Government of the United States
of America as Represented by the Secretary of the Navy
(Washington, DC)
|
Family
ID: |
67477367 |
Appl.
No.: |
15/486,481 |
Filed: |
April 13, 2017 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64F
1/06 (20130101); B64C 39/024 (20130101); B64C
2201/084 (20130101) |
Current International
Class: |
B64F
1/06 (20060101); F41B 3/03 (20060101); B64C
39/02 (20060101) |
References Cited
[Referenced By]
U.S. Patent Documents
Other References
Wikipedia, Compound Bow, article, Mar. 28, 2017, United States
https://en.wikipedia.org/wiki/Compound_bow. cited by
applicant.
|
Primary Examiner: O'Hara; Brian M
Attorney, Agent or Firm: Sauz; Jimmy M.
Government Interests
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT
The invention described herein may be manufactured and used by or
for the government of the United States of America for governmental
purposes without the payment of any royalties thereon or therefor.
Claims
What is claimed as new and desired to be protected by Letters
Patent is set forth in the appended claims:
1. A method for converting a launcher from a stowed configuration
into a launch configuration, the method comprising the steps:
providing the launcher in the stowed configuration, said launcher
comprising: (1) a launch rail having a forward beam portion and an
aft beam portion, said forward beam portion being hingedly coupled
to said aft beam portion via a hinge and is folded onto said aft
beam portion, such that said forward beam portion is stacked on
said aft beam portion, and (2) a pair of pulley drivers hingedly
coupled to a proximal end of said launch rail, each being folded
against an associated lateral side of said launch rail; unfolding
said launch rail by pivoting said forward beam portion away from
said aft beam portion; unfolding said pair of pulley drivers by
pivoting said pair of pulley drivers away from said launch rail and
having said pair of pulley drivers substantially orthogonal to said
launch rail, such that said pulley drivers are substantially
aligned and abutting each other; and installing a leg at said
distal end of said launch rail.
2. The method according to claim 1, wherein each of said pair of
pulley drivers comprises a spring compression cam pulley; and
wherein said method further comprises the step of installing a
spring compression cable to said pair of pulley drivers by having
each opposing end of said spring compression cable couple to an
associated one of said spring compression cam pulleys.
3. The method according to claim 1, further comprising the steps
of: providing a quick release pin for said launch rail; and
securing said launch rail in said launch configuration by
installing said quick release pin on said hinge of said launch
rail.
4. The method according to claim 1, further comprising the step of:
providing a fastening latch for each of said pulley drivers; and
securing said pair of pulley drivers in said launch configuration
by installing one of said fastening latches on each of said pulley
drivers.
5. The method according to claim 1, wherein said launcher in said
stowed configuration further comprises a pair of forward beam
wheels rotatably coupled to said aft beam portion of said launch
rail; and wherein the method further comprises the step of removing
said pair of forward beam wheels from said launch rail.
6. The method according to claim 1, wherein each of said pair of
pulley drivers comprises an adjustable leveling mount; and wherein
the method further comprises the step of deploying said adjustable
leveling mount for each of said pair of pulley drivers.
7. A method for converting a launcher from a stowed configuration
into a launch configuration, the method comprising the steps:
providing the launcher in the stowed configuration, said launcher
comprising: (1) a launch rail having a forward beam portion and an
aft beam portion, said forward beam portion being hingedly coupled
to said aft beam portion via a hinge and is folded onto said aft
beam portion, such that said forward beam portion is stacked on
said aft beam portion; (2) a pair of pulley drivers hingedly
coupled to a proximal end of said launch rail, each being folded
against an associated lateral side of said launch rail; (3) a pair
of forward beam wheels rotatably coupled to said aft beam portion
of said launch rail; and (4) an adjustable leveling mount coupled
to each of said pair of pulley drivers; unfolding said launch rail
by pivoting said forward beam portion away from said aft beam
portion; unfolding said pair of pulley drivers away from said
launch rail and having said pair of pulley drivers substantially
orthogonal to said launch rail, such that said pulley drivers are
substantially aligned and abutting each other; lifting a distal end
of said launch rail; installing a leg at said distal end of said
launch rail; removing said pair of forward beam wheels from said
launch rail; and deploying said adjustable leveling mount for each
of said pair of pulley drivers.
8. The method according to claim 7, wherein each of said pair of
pulley drivers comprises a spring compression cam pulley; and
wherein said method further comprises the step of installing a
spring compression cable to said pair of pulley drivers by having
each opposing end of said spring compression cable couple to an
associated one of said spring compression cam pulleys.
9. The method according to claim 7, further comprising the step of:
providing a quick release pin for said launch rail; and securing
said launch rail in said launch configuration by installing said
quick release pin on said hinge of said launch rail.
10. The method according to claim 7, further comprising the step
of: providing a fastening latch for each of said pulley drivers;
and securing said pair of pulley drivers in said launch
configuration by installing one of said fastening latches on each
of said pulley drivers.
11. A method for launching an unmanned aircraft from a launcher
having a pair of pulley drivers and a cable and pulley system, the
method comprising the steps: providing a launcher having: (1) a
launch rail; (2) a carriage slidably engaged with said launch rail;
(3) a pair of pulley drivers hingedly coupled to a proximal end of
said launch rail and each comprising a slider assembly and one or
more compression springs, said pair of pulley drivers being adapted
to create pulley drive forces; and (4) a cable and pulley system
for converting both said pulley drive forces into a launching force
for said carriage; wherein said cable and pulley system comprises:
(1) a winch; (2) a plurality of launch rail pulleys; (3) a
centering pulley sheave located on said carriage; (4) a pair of
drive cam pulleys, each being rotatably coupled to an associated
one of said slider assemblies; (5) a pair of spring compression cam
pulleys axially fixed with said drive cam pulleys; (6) one or more
drive cables in physical communication with said winch, said
plurality of launch rail pulleys, said pair of drive cam pulleys,
and said centering pulley sheave, and (7) spring compression cam
cable having opposing ends coupled to said spring compression cam
pulleys; mounting an unmanned aircraft on said carriage; actuating
said winch to retract said one or more drive cables, said
retraction causing said one or more drive cables to rotate said
drive cam pulleys and said pair of spring compression cam pulleys,
said rotation of said spring compression cam pulleys resulting with
a winding of said spring compression cam cable and a biasing of
said one or more compression springs by said slider assemblies; and
launching, by said pair of pulley drivers, by releasing a quick
release fastener coupled to an attachment point of said
carriage.
12. The method according to claim 11, wherein said cable and pulley
system further comprises a brake pulley support assembly positioned
near a distal end of said launch rail, said brake pulley support
assembly, comprising: a first pair of brake pulleys and a second
pair of brake pulleys.
13. The method according to claim 11, wherein said carriage
comprises: a carriage body and a pair of carriage arms, each being
rotatably coupled to a left side and a right side respectively, of
said carriage body; and wherein said mounting of said unmanned
aircraft further comprises the step of: rotating said pair of
carriage arms against a fusalege of said unmanned aircraft, such
that said pair of carriage arms are releasably engaged with said
unmanned aircraft.
14. The method according to claim 11, wherein said release of said
quick release fastener causes said carriage to launch and said
compression springs to expand, converting said pulley drive forces
into said launching force to drive said one or more drive cables
and said carriage along said launch rail.
15. The method according to claim 11, wherein said plurality of
launch rail pulleys include: (1) a pair of launch rail forward
pulleys mounted alongside each other at said distal end of said
launch rail; and (2) a pair of launch rail aft pulleys mounted
alongside each other near said proximal end of said launch
rail.
16. The method according to claim 15, wherein said cable and pulley
system further comprises: a pulley block slidably engaged beneath
said launch rail, comprising a pair of pulley block pulleys mounted
alongside each other and a centering pulley block pulley mounted
substantially at a centerline on said pulley block.
17. The method according to claim 16, wherein said cable and pulley
system further comprises a winch cable interface; and wherein said
winch comprises a winch cable coupled to said winch cable
interface.
18. The method according to claim 17, wherein said one or more
drive cables include: (1) a first drive cable having each opposing
end coupled to an associated one of said drive cam pulleys, and
from there extending around said pair of launch rail aft pulleys,
said first drive cable also having an intermediate portion reeved
around said centering pulley block pulley; and (2) a second drive
cable having both opposing ends coupled to said winch cable
interface, and from there extending around said pair of pulley
block pulleys and further extending around said pair of launch rail
forward pulleys at said distal end of said launch rail, said second
drive cable also having an intermediate portion reeved around said
centering pulley sheave of said carriage.
19. The method according to claim 11, further comprising: a manual
winch mounted near said proximal end of said launch rail, said
manual winch comprising: a drum, a manual winch cable, and said
quick release fastener, said quick release fastener being adapted
to releasably couple to an attachment point of said carriage.
20. The launcher according to claim 11, wherein said launch rail
comprises a forward beam portion and an aft beam portion, said
forward beam portion being hingedly coupled to said aft beam
portion; and wherein said pair of pulley drivers are also hingedly
coupled to said distal end of said launch rail, such that said
launch rail and said pair of pulley drivers have a stowed
configuration and a launch configuration.
Description
FIELD
The present disclosure relates generally to methods and apparatuses
for launching an unmanned aircraft such as an unmanned aerial
vehicle (UAV) or unmanned aerial system (UAS).
BACKGROUND
Unmanned aircraft such as UAVs and UASs are aircrafts that lack a
pilot onboard. Unmanned aircraft are typically operated under
remote control by a human operator or autonomously by an onboard
computer. Unlike manned aircraft, UAVs are often used for military
and commercial applications in environments that are unacceptably
too costly and/or dangerous to humans. Examples of such
applications may include policing, surveillance, and testing. UAVs,
for instance, may be used to detect enemy threats autonomously from
aerial vantage points.
Launching mechanisms for UAVs generally require a large open space.
Thus, it is often desirable to have a launcher designed to propel
the UAV within a relatively short distance. In order for a UAV
launcher to achieve the smallest possible launch distance, energy
must be applied to the aircraft within the smallest period of time
and without exceeding the aircraft's acceleration limits. This is
generally accomplished by applying a constant force to the aircraft
uniformly over the launch distance. While the use of energy storage
devices such as pneumatic cylinders have been used to launch
unmanned aircraft, use of such storage devices generally results
with energy increasing linearly with displacement.
Therefore, based on the foregoing, a need exists that overcomes
these deficiencies. The present disclosure solves these
deficiencies and generally represents a new and useful innovation
in the realm of launchers for unmanned aircraft.
SUMMARY OF ILLUSTRATIVE EMBODIMENTS
To minimize the limitations in the related art and other
limitations that will become apparent upon reading and
understanding the present specification, the following discloses
embodiments of a new and useful launcher for an unmanned aircraft
such as unmanned aircraft vehicles (UAVs) and unmanned aircraft
systems (UASs) and the methods of use thereof.
One embodiment may be a launcher for an unmanned aircraft,
comprising: a launch rail having at least one leg; a carriage
slidably engaged with the launch rail; a pair of pulley drivers
coupled to a proximal end of the launch rail, each comprising a
slider assembly, wherein the pair of pulley drivers may be adapted
to produce a pair of pulley drive forces to drive the slider
assemblies; and a cable and pulley system, comprising: a pair of
launch rail forward pulleys mounted alongside each other at a
distal end of the launch rail; a pair of launch rail aft pulleys
mounted alongside each other near the proximal end of the launch
rail; a pulley block slidably engaged beneath the launch rail,
comprising a pair of pulley block pulleys mounted alongside each
other and a centering pulley block pulley mounted substantially at
a centerline on the pulley block; a winch cable interface slidably
engaged beneath the launch rail; a centering pulley sheave located
on the carriage; a pair of drive cam pulleys, each being rotatably
coupled to an associated one of the slider assemblies; a first
drive cable having each opposing end coupled to an associated one
of the drive cam pulleys, and from there extending around the pair
of launch rail aft pulleys, the first drive cable also having an
intermediate portion reeved around the centering pulley block
pulley; a second drive cable having both opposing ends coupled to
the winch cable interface, and from there extending around the pair
of pulley block pulleys and further extending around the pair of
launch rail forward pulleys at the distal end of the launch rail,
the second drive cable also having an intermediate portion reeved
around the centering pulley sheave of the carriage; and a winch
mounted at the distal end of the launch rail, the winch comprising
a winch cable coupled to the winch cable interface. Each of the
pair of pulley drivers may further comprise: one or more linear
bearing shafts and one or more compression springs; wherein the one
or more compression springs may be adapted to produce the pulley
drive forces by biasing the slider assemblies linearly along the
one or more linear bearing shafts. The cable and pulley system may
further comprise: a pair of spring compression cam pulleys, each
being axially fixed to an associated one of the drive cam pulleys
and rotatably coupled to an associated one of the slider
assemblies, such that when the drive cam pulleys rotate, the spring
compression cam pulleys also rotate; and a spring compression cable
having each opposing end coupled to an associated one of the spring
compression cam pulleys. The cable and pulley system may further
comprise a brake pulley support assembly positioned near a distal
end of the launch rail, the brake pulley support assembly,
comprising: a first pair of brake pulleys and a second pair of
brake pulleys. The launch rail may comprise a forward beam portion
and an aft beam portion, the forward beam portion being hingedly
coupled to the aft beam portion; and wherein the pair of pulley
drivers may also be hingedly coupled to the distal end of the
launch rail, such that the launch rail and the pair of pulley
drivers have a stowed configuration and a launch configuration. The
carriage may comprise: a carriage body and a pair of carriage arms,
each being rotatably coupled to a left side and a right side of the
carriage body for releasably supporting the unmanned aircraft. The
launcher may further comprise: a manual winch mounted near the
proximal end of the launch rail, the manual winch comprising: a
drum, a manual winch cable, and a quick release fastener, the quick
release fastener being adapted to releasably couple to an
attachment point of the carriage. The at least one leg may be
movably coupled to a platform of a vessel.
Another embodiment may be a launcher for an unmanned aircraft,
comprising: a launch rail having a track and at least one leg
coupled to a distal end of the launch rail; a carriage slidably
engaged with the launch rail and adapted to move linearly along the
track; a pair of pulley drivers coupled to a proximal end of the
launch rail, each of the pulley drivers comprising a slider
assembly, wherein the pair of pulley drivers are oriented away from
each other and adapted to produce a pair of opposing pulley drive
forces in opposing directions relative to each other in order to
propel the pair of slider assemblies away from each other; and a
cable and pulley system for converting the pair of opposing pulley
drive forces into a launching force for the carriage, the cable and
pulley system being operatively associated with the pair of pulley
drivers and the carriage, comprising: a pair of launch rail forward
pulleys mounted alongside each other at the distal end of the
launch rail; a pair of launch rail aft pulleys mounted alongside
each other near the proximal end of the launch rail; a pulley block
slidably engaged beneath the launch rail, comprising a pair of
pulley block pulleys mounted alongside each other and a centering
pulley block pulley mounted substantially at a centerline on the
pulley block; a winch cable interface slidably engaged beneath the
launch rail, the winch cable interface being disposed between the
pulley block and the pair of launch rail forward pulleys; a
centering pulley sheave located on the carriage; a pair of drive
cam pulleys, each being rotatably coupled to an associated one of
the slider assemblies; a first drive cable having each opposing end
coupled to an associated one of the drive cam pulleys, and from
there extending around the pair of launch rail aft pulleys, the
first drive cable also having an intermediate portion reeved around
the centering pulley block pulley; a second drive cable having both
opposing ends coupled to the winch cable interface, and from there
extending around the pair of pulley block pulleys and further
extending around the pair of launch rail forward pulleys at the
distal end of the launch rail, the second drive cable also having
an intermediate portion reeved around the centering pulley sheave;
and a winch mounted at the distal end of the launch rail, the winch
comprising a drum and a winch cable windable thereon, the winch
cable also being coupled to the winch cable interface. Each of the
pair of pulley drivers may further comprise: one or more linear
bearing shafts and one or more compression springs; and wherein the
one or more compression springs may be adapted to produce the
pulley drive forces by biasing the slider assemblies linearly along
the one or more linear bearing shafts. The cable and pulley system
may further comprise: a pair of spring compression cam pulleys,
each being axially fixed to an associated one of the drive cam
pulleys and rotatably coupled to an associated one of the slider
assemblies, such that when the drive cam pulleys rotate, the spring
compression cam pulleys also rotate; and a spring compression cable
having each opposing end coupled to an associated one of the spring
compression cam pulleys. The cable and pulley system may further
comprise a brake pulley support assembly positioned near a distal
end of the launch rail, the brake pulley support assembly,
comprising: a first pair of brake pulleys and a second pair of
brake pulleys; and wherein the second drive cable may extend
in-between each of the first pair of brake pulleys and may further
extends between the first pair and the second pair of brake pulleys
and around the second pair of brake pulleys. The launch rail may
comprise a forward beam portion and an aft beam portion, the
forward beam portion being hingedly coupled to the aft beam
portion; and wherein the pair of pulley drivers may also be
hingedly coupled to the distal end of the launch rail, such that
the launch rail and the pair of pulley drivers have a stowed
configuration and a launch configuration. The launcher for an
unmanned aircraft may further comprise: a manual winch mounted near
the proximal end of the launch rail, the manual winch comprising: a
drum, a manual winch cable, and a quick release fastener, the quick
release fastener being adapted to releasably couple to an
attachment point on the carriage.
Another embodiment may be a launcher for an unmanned aircraft,
comprising: a launch rail having a track and at least one leg
removeably coupled to a distal end of the launch rail; a carriage
slidably engaged on the launch rail and adapted to move linearly
along the track; a first pulley driver hingedly and orthogonally
coupled to a proximal end of the launch rail, the first pulley
driver comprising a first slider assembly, one or more first linear
bearing shafts, and one or more first compression springs, the one
or more first compression springs being adapted to provide biasing
to the first slider assembly linearly along the one or more first
linear bearing shafts to produce a first pulley drive force; a
second pulley driver hingedly and orthogonally coupled to a
proximal end of the launch rail, the second pulley driver
comprising a second slider assembly, one or more second linear
bearing shafts, and one or more second compression springs, the one
or more compression springs being adapted to provide biasing to the
second slider assembly linearly along the one or more second linear
bearing shafts to produce a second pulley drive force; wherein the
first pulley driver and the second pulley driver may be oriented
away from each other and may be adapted to produce the first pulley
driver force and the second pulley drive force, respectively, in
opposing directions relative to each other to propel the first
slider assembly and the second slider assembly away from each
other; and a cable and pulley system for converting both the first
pulley drive force and the second pulley drive force into a
launching force for the carriage, the cable and pulley system being
operatively associated with the first pulley driver, the second
pulley driver, and the carriage, comprising: a pair of launch rail
forward pulleys mounted alongside each other at the distal end of
the launch rail; a pair of launch rail aft pulleys mounted
alongside each other near the proximal end of the launch rail; a
pulley block slidably engaged beneath the launch rail, comprising a
pair of pulley block pulleys mounted alongside each other and a
centering pulley block pulley mounted substantially at a centerline
on the pulley block; a winch cable interface slidably engaged
beneath the launch rail, the winch cable interface being disposed
between the pulley block and the pair of launch rail forward
pulleys; a centering pulley sheave located on the carriage; a first
drive cam pulley rotatably coupled to the first slider assembly; a
second drive cam pulley rotatably coupled to the second slider
assembly; a first drive cable having each opposing end coupled to
the first drive cam pulley and the second drive cam pulley, and
from there extending around the pair of launch rail aft pulleys,
the first drive cable also having an intermediate portion reeved
around the centering pulley block pulley; a second drive cable
having both ends end coupled to the winch cable interface, and from
there extending around the pair of pulley block pulleys and further
extending around the pair of launch rail forward pulleys at the
distal end of the launch rail, the second drive cable also having
an intermediate portion reeved around the centering pulley sheave
on the carriage; and a winch mounted at the distal end of the
launch rail, the winch comprising a drum and a winch cable windable
thereon, the winch cable also being coupled to the winch cable
interface. The cable and pulley system may further comprise: a
first spring compression cam pulley axially fixed to the first
drive cam pulley and rotatably coupled to the first slider
assembly, such that when the first drive cam pulley rotates, the
spring compression cam pulley also rotates; a second spring
compression cam pulley axially fixed to the second drive cam pulley
and rotatably coupled to the second slider assembly, such that when
the second drive cam pulley rotates, the spring compression cam
pulley also rotates; and a spring compression cable having a first
end coupled to the first spring compression cam pulley and a second
end coupled to the second spring compression cam. The cable and
pulley system may further comprise a brake pulley support assembly
positioned near a distal end of the launch rail, the brake pulley
support assembly, comprising: a first pair of brake pulleys and a
second pair of brake pulleys; and wherein the drive cable extends
in-between each of the first pair of brake pulleys and further
extends between the first pair and the second pair of brake pulleys
and around the second pair of brake pulleys. The carriage may
comprise: a left carriage arm portion, a right carriage arm
portion, and a carriage body; wherein the left carriage portion and
the right carriage portion may be rotatably coupled to a left side
and a right side of the carriage body, respectively, for releasably
supporting the unmanned aircraft during a launch. The launch rail
may comprise a forward beam portion and an aft beam portion, the
forward beam portion being hingedly coupled to the aft beam
portion; and wherein the pair of pulley drivers may also be
hingedly coupled to the distal end of the launch rail, such that
the launch rail and the pair of pulley drivers have a stowed
configuration and a launch configuration. The launcher may further
comprise: a manual winch mounted near the proximal end of the
launch rail, the manual winch comprising: a drum, a manual winch
cable, and a quick release fastener, the quick release fastener
being adapted to releasably couple to the carriage.
Another embodiment may be a method for converting a launcher from a
stowed configuration into a launch configuration, the method
comprising the steps: providing a launcher in a stowed
configuration, the launcher comprising: (1) a launch rail having a
forward beam portion and an aft beam portion, the forward beam
portion being hingedly coupled to the aft beam portion via a hinge
and is folded onto the aft beam portion, such that the forward beam
portion is stacked on the aft beam portion, and (2) a pair of
pulley drivers hingedly coupled to a proximal end of the launch
rail, each being folded against an associated lateral side of the
launch rail; prompting a user to unfold the launch rail by pivoting
the forward beam portion away from the aft beam portion; prompting
the user to unfold the pair of pulley drivers away from the launch
rail to have the pair of pulley drivers substantially orthogonal to
the launch rail, such that the pulley drivers are substantially
aligned and abutting each other; and prompting the user to install
a leg at the distal end of the launch rail. Each of the pair of
pulley drivers may comprise a spring compression cam pulley; and
wherein the method may further comprises the step of prompting the
user to install a spring compression cable to the pair of pulley
drivers by having each opposing end of the spring compression cable
couple to an associated one of the spring compression cam pulleys.
The method may further comprise the steps of: providing a quick
release pin for the launch rail; and prompting the user to secure
the launch rail in the unfolded configuration by installing the
quick release pin on the hinge of the launch rail. The method may
further comprise the step of: providing a fastening latch for each
of the pulley drivers; and prompting the user to secure the pair of
pulley drivers in the unfolded configuration by installing a
fastening latch for each of the pulley drivers. The launcher in the
stowed configuration may further comprise a pair of forward beam
wheels rotatably coupled to the aft beam portion of the launch
rail; and wherein the method may further comprise the step of
prompting the user to remove the pair of forward beam wheels from
the launch rail. Each of the pair of pulley drivers may comprise an
adjustable leveling mount; and wherein the method further comprises
the step of prompting the user to deploy the adjustable leveling
mount for each of the pair of pulley drivers.
Another embodiment may be a method for converting a launcher from a
stowed configuration into a launch configuration, the method
comprising the steps: providing a launcher in a stowed
configuration, the launcher comprising: (1) a launch rail having a
forward beam portion and an aft beam portion, the forward beam
portion being hingedly coupled to the aft beam portion via a hinge
and is folded onto the aft beam portion, such that the forward beam
portion is stacked on the aft beam portion; (2) a pair of pulley
drivers hingedly coupled to a proximal end of the launch rail, each
being folded against an associated lateral side of the launch rail;
(3) a pair of forward beam wheels rotatably coupled to the aft beam
portion of the launch rail; and (4) an adjustable leveling mount
coupled to each of the pair of pulley drivers; prompting a user to
unfold the launch rail by pivoting the forward beam portion away
from the aft beam portion; prompting the user to unfold the pair of
pulley drivers away from the launch rail and having the pair of
pulley drivers substantially orthogonal to the launch rail, such
that the pulley drivers are substantially aligned and abutting each
other; prompting the user to lift a distal end of the launch rail;
and prompting the user to install a leg at the distal end of the
launch rail; prompting the user to remove the pair of forward beam
wheels from the launch rail; and prompting the user to deploy the
adjustable leveling mount for each of the pair of pulley drivers.
Each of the pair of pulley drivers may comprise a spring
compression cam pulley; and wherein the method may further comprise
the step of prompting the user to install a spring compression
cable to the pair of pulley drivers by having each opposing end of
the spring compression cable couple to an associated one of the
spring compression cam pulleys. The method may further comprise the
step of: providing a quick release pin for the launch rail; and
prompting the user to secure the launch rail in the unfolded
configuration by installing the quick release pin on the hinge of
the launch rail. The method may further comprise the step of:
providing a fastening latch for each of the pulley drivers; and
prompting the user to secure the pair of pulley drivers in the
unfolded configuration by installing a fastening latch for each of
the pulley drivers.
Another embodiment may be a method for launching an unmanned
aircraft from a launcher having a pair of pulley drivers and a
cable and pulley system, the method comprising the steps: providing
a launcher having: (1) a launch rail; (2) a carriage slidably
engaged with the launch rail; (3) a pair of pulley drivers hingedly
coupled to a proximal end of the launch rail and each comprising a
slider assembly and one or more compression springs, the pair of
pulley drivers being adapted to create pulley drive forces; and (3)
a cable and pulley system for converting both the pulley drive
forces into a launching force for the carriage; wherein the cable
and pulley system comprises: (1) a winch; (2) a plurality of launch
rail pulleys; (3) a centering pulley sheave located on the
carriage; (3) a pair of drive cam pulleys, each being rotatably
coupled to an associated one of the slider assemblies; (4) a pair
of spring compression cam pulleys axially fixed with the drive cam
pulleys; (5) one or more drive cables in physical communication
with the winch, the plurality of launch rail pulleys, the pair of
drive cam pulleys, and the centering pulley sheave, and (6) spring
compression cam cable having opposing ends coupled to the spring
compression cam pulleys; mounting an unmanned aircraft on the
carriage; (7) actuating the winch to retract the one or more drive
cables, the retraction causing the one or more drive cables to
rotate the drive cam pulleys and the pair of spring compression cam
pulleys, the rotation of the spring compression cam pulleys
resulting with a winding of the spring compression cam cable and a
biasing of the one or more compression springs by the slider
assemblies; and (8) launching, by the pair of pulley drivers, by
unfastening a quick release fastener coupled to the carriage. The
cable and pulley system may further comprise a brake pulley support
assembly positioned near a distal end of the launch rail, the brake
pulley support assembly, comprising: a first pair of brake pulleys
and a second pair of brake pulleys. The carriage may comprise: a
carriage body and a pair of carriage arms, each being rotatably
coupled to a left side and a right side of the carriage body; and
wherein the mounting of the unmanned aircraft may further comprise
the step of: prompting a user to rotate the pair of carriage arms
against a fusalege of the unmanned aircraft, such that the pair of
carriage arms are releasably engaged with the unmanned aircraft.
The actuation of the quick release fastener may cause the carriage
to be released and the compression springs to expand, converting
the pulley drive forces into the launching force to drive the one
or more drive cables and the carriage along the launch rail. The
plurality of launch rail pulleys may include: (1) a pair of launch
rail forward pulleys mounted alongside each other at the distal end
of the launch rail; and (2) a pair of launch rail aft pulleys
mounted alongside each other near the proximal end of the launch
rail. The cable and pulley system may further comprise: a pulley
block slidably engaged beneath the launch rail, comprising a pair
of pulley block pulleys mounted alongside each other and a
centering pulley block pulley mounted substantially at a centerline
on the pulley block. The cable and pulley system may further
comprise a winch cable interface; wherein the winch may comprise a
winch cable coupled to the winch cable interface. The one or more
drive cables may include: (1) a first drive cable having each
opposing end coupled to an associated one of the drive cam pulleys,
and from there extending around the pair of launch rail aft
pulleys, the first drive cable also having an intermediate portion
reeved around the centering pulley block pulley; and (2) a second
drive cable having both opposing ends coupled to the winch cable
interface, and from there extending around the pair of pulley block
pulleys and further extending around the pair of launch rail
forward pulleys at the distal end of the launch rail, the second
drive cable also having an intermediate portion reeved around the
centering pulley sheave of the carriage. The method may further
comprise: a manual winch mounted near the proximal end of the
launch rail, the manual winch comprising: a drum, a manual winch
cable, and the quick release fastener, the quick release fastener
being adapted to releasably couple to an attachment point of the
carriage. The launch rail may comprise a forward beam portion and
an aft beam portion, the forward beam portion being hingedly
coupled to the aft beam portion; and wherein the pair of pulley
drivers may be hingedly coupled to the distal end of the launch
rail, such that the launch rail and the pair of pulley drivers have
a stowed configuration and a launch configuration.
The advantage of the launcher disclosed herein generally lies in
the geometry and functionality of the pulley drivers, each of which
may comprise axially aligned, counter opposed compression springs.
These compression springs may be compressed via the sliding or
translating of slider assemblies in conjunction with the rotation
of a pair of spring compression cam pulleys. Each spring
compression cam pulley may be rotationally opposed to each other
and may be axially fixed to an associated larger drive cam pulley.
Thus, as a drive cable is drawn, the spring compression cam
pulleys, slaved to each other, may retract the spring compression
cable, and may compress the compression springs to store energy.
Upon launch, this stored energy may be released as the drive cable
is allowed to retract. A cable and pulley system may utilize the
compression spring axis, drive cable, and spring compression cable
in parallel, resulting with counter opposing moments and pure
linear force on the compression springs and supporting assembly.
This may isolate the high force, strength area to a small portion
of the launcher as opposed to the entire length of the pulley
drivers.
It is an object to provide a launcher with a mechanism to regulate
tension. In various embodiments, the launcher may regulate tension
through leverage ratios between cams, such as those found in
recreational compound archery bows where energy is stored through
elastic limb deflection. Because scaling a compound bow with use of
a UAV may prove impractical due to size and material property
limitations, it may be preferred to utilize compression springs in
conjunction with cam tension. As a result, cam tension in lieu of
limb deflection may allow sufficient energy storage and constant
force regulation.
It is an object to provide a launcher for UAV with the capability
of folding or disassembling the launcher into smaller, easy to
assemble subcomponents. Thus, the UAV launcher may be portable and
easier to transport or store.
It is an object to overcome the limitations of the prior art.
These, as well as other components, steps, features, objects,
benefits, and advantages, will now become clear from a review of
the following detailed description of illustrative embodiments, the
accompanying drawings, and the claims.
BRIEF DESCRIPTION OF THE DRAWINGS
The drawings are illustrative embodiments. They do not illustrate
all embodiments. They do not set forth all embodiments. Other
embodiments may be used in addition or instead. Details, which may
be apparent or unnecessary, may be omitted to save space or for
more effective illustration. Some embodiments may be practiced with
additional components or steps and/or without all of the components
or steps, which are illustrated. When the same numeral appears in
different drawings, it is intended to refer to the same or like
components or steps.
FIG. 1 is an illustration of an exploded, perspective view of one
embodiment of a launcher for an unmanned aircraft.
FIGS. 2A and 2B are illustrations of exploded, side views of some
embodiments of the pulley drivers.
FIGS. 3A and 3B are illustrations of exploded, perspective views of
some embodiments of the slider assemblies.
FIG. 4 is an illustration of an exploded, perspective view of one
embodiment of the launch rail.
FIG. 5 is an illustration of an exploded, perspective view of one
embodiment of the carriage.
FIG. 6 is a flow diagram of one embodiment of a method for a launch
sequence of the launcher.
FIGS. 7A to 7F are illustrations of perspective views of one
embodiment of the launcher and shows the launcher in operation.
FIGS. 8A to 8F are illustrations of bottom plan views of one
embodiment of the launcher and shows the launcher in operation (as
depicted in FIGS. 7A to 7F).
FIG. 9 is a flow diagram of one embodiment of a method for
converting the launcher from a stowed configuration to a launch
configuration.
FIGS. 10A to 10C are illustrations of perspective views of one
embodiment of the launcher and shows the launcher in a stowed
configuration, a partially-folded configuration, and a launch
configuration.
FIGS. 11A and 11B are illustrations of another embodiment of the
launcher configured to removably attach onto a platform of a vessel
and show the launcher in a stowed configuration and launch
configuration.
FIGS. 12A and 12B are graphs of the carriage velocity and carriage
acceleration as a function of displacement for various embodiments
of the launcher disclosed herein.
DETAILED DESCRIPTION OF ILLUSTRATIVE EMBODIMENTS
In the following detailed description, numerous specific details
are set forth in order to provide a thorough understanding of
various aspects of one or more embodiments of a launcher for an
unmanned aircraft. However, these embodiments may be practiced
without some or all of these specific details. In other instances,
well-known methods, procedures, and/or components have not been
described in detail so as not to unnecessarily obscure the aspects
of these embodiments.
Before the embodiments are disclosed and described, it is to be
understood that these embodiments are not limited to the particular
structures, process steps, or materials disclosed herein, but is
extended to equivalents thereof as would be recognized by those
ordinarily skilled in the relevant arts. It should also be
understood that terminology used herein is used for the purpose of
describing particular embodiments only and is not intended to be
limiting.
Reference throughout this specification to "one embodiment," "an
embodiment," or "another embodiment" may mean that a particular
feature, structure, or characteristic described in connection with
the embodiment may be included in at least one embodiment of the
present disclosure. Thus, appearances of the phrases "in one
embodiment" or "in an embodiment" in various places throughout this
specification may not necessarily refer to the same embodiment.
Furthermore, the described features, structures, or characteristics
may be combined in any suitable manner in various embodiments. In
the following description, numerous specific details are provided,
such as examples of materials, fasteners, sizes, lengths, widths,
shapes, etc . . . , to provide a thorough understanding of the
embodiments. One skilled in the relevant art will recognize,
however, that the scope of protection can be practiced without one
or more of the specific details, or with other methods, components,
materials, etc. . . . In other instances, well-known structures,
materials, or operations are generally not shown or described in
detail to avoid obscuring aspects of the disclosure.
Definitions
In the following description, certain terminology is used to
describe certain features of the embodiments of a launcher for an
unmanned aircraft. For example, as used herein, unless otherwise
specified, the terms "unmanned aircraft," "aircraft," "unmanned
aerial vehicle," "unmanned aerial system," "UAS," "UAV," and
"drone" generally refer to any aircraft capable of being piloted
without having a human pilot onboard the aircraft. These aircraft
vehicles may be controlled remotely or autonomously via an onboard
computer or the like.
As used herein, the terms "rail" and "launch rail" refer to one or
more bars (e.g., pair of bars) or beams that provide the running
surface(s) for launching or propelling an unmanned aircraft into
flight.
As used herein, the term "pulley" generally refers to any wheel or
eccentric driven by or driving a cable, rope, or the like and is
used to deliver force to a machine or another cable or belt. A
pulley may also include wheels that rotate and serve to change the
direction of or to transmit force (as when one end of the cable is
pulled to raise a weight at the other end). In various embodiments,
a pulley may include a single wheel or eccentric element, and also
may include an assembly of one or more such components. In various
embodiments, a pulley wheel typically defines a groove, or string
track, in which to receive a cable rigging element, that is
concentric with an axis of rotation of the wheel. An eccentric may
define a groove, or string track, in which to receive a rigging
element, that is spaced by a variable radius from the axis of
rotation of the eccentric. Sometimes, an eccentric or wheel may be
identified as a "cam" substantially in accordance with its ordinary
dictionary meaning. As disclosed herein, a pulley, or pulley
assembly, may also be sometimes referred to as a "cam".
As used herein, the term "launch rail pulley" generally refers to
any wheel or eccentric mounted at one or more areas of a launch
rail and configured to drive or be driven by a cable, rope, or the
like. Examples of launch rail pulleys may include, without
limitation, launch rail forward pulleys and launch rail aft
pulleys.
As used herein, the terms "prompt" or "prompting" may refer to any
act that assists or encourages a user to perform a certain act. The
terms "prompt" or "prompting" may also refer to any passive action
or inaction that allows or permits a user to perform that
particular act. For example, in one embodiment, "prompt" or
"prompting" may include providing instructions, directions, or
guidance to a user via an instruction manual or equivalent, so as
to convert the launcher from a stowed configuration into a launch
configuration and vice versa. In another embodiment, "prompt" or
"prompting" may also include providing instructions, directions, or
guidance to a user via an instruction manual or equivalent, so as
to prepare the launcher for launching an unmanned aircraft.
As used herein, the term "substantially" refers to the complete, or
nearly complete, extent or degree of an action, characteristic,
property, state, structure, item, or result. As an arbitrary
example, an object that is "substantially" enclosed would mean that
the object is either completely enclosed or nearly completely
enclosed. The exact allowable degree of deviation from absolute
completeness may in some cases depend on the specific context.
However, generally speaking, the nearness of completion will be so
as to have the same overall result as if absolute and total
completion were obtained.
The use of "substantially" is equally applicable when used in a
negative connotation to refer to the complete or near complete lack
of an action, characteristic, property, state, structure, item, or
result. As another arbitrary example, a composition that is
"substantially free of" particles would either completely lack
particles, or so nearly completely lack particles that the effect
would be the same as if it completely lacked particles. In other
words, a composition that is "substantially free of" an ingredient
or element may still actually contain such item as long as there is
no measurable effect thereof.
As used herein, the term "approximately" may refer to a range of
values of +10% of a specific value. For example, the expression
"approximately 150 inches" may comprise the values of 150
inches.+-.10%, i.e. the values from 135 inches to 165 inches. In
other embodiments, the term "approximately" may also refer to a
range of values of .+-.15% of a specific value.
As used herein, the term "about" is used to provide flexibility to
a numerical range endpoint by providing that a given value may be
"a little above" or "a little below" the endpoint. In some cases,
the term "about" is to include a range of not more than about two
inches of deviation.
Distances, forces, weights, amounts, and other numerical data may
be expressed or presented herein in a range format. It is to be
understood that such a range format is used merely for convenience
and brevity and thus should be interpreted flexibly to include not
only the numerical values explicitly recited as the limits of the
range, but also to include all the individual numerical values or
sub-ranges encompassed within that range as if each numerical value
and sub-range is explicitly recited.
As an illustration, a numerical range of "about 1 inch to about 5
inches" should be interpreted to include not only the explicitly
recited values of about 1 inch to about 5 inches, but also include
individual values and sub-ranges within the indicated range. Thus,
included in this numerical range are individual values such as 2,
3, and 4 and sub-ranges such as from 1-3, from 2-4, and from
3-5.
This same principle applies to ranges reciting only one numerical
value and should apply regardless of the breadth of the range or
the characteristics being described.
As used herein in this disclosure, the singular forms "a" and "the"
may include plural referents, unless the context clearly dictates
otherwise. Thus, for example, reference to a "pulley" can include
reference to one or more of such pulleys.
This disclosure relates generally to apparatuses for launching an
unmanned aircraft such as an unmanned aerial vehicle (UAV) or
unmanned aerial system (UAS). Embodiments of the launcher may be
designed to propel the UAV within a relatively short distance and
may be accomplished by applying energy to the aircraft in the
smallest period of time and without exceeding the aircraft's
acceleration limits. This may be accomplished by applying a
constant force to the aircraft uniformly over the launch
distance.
The advantage of the launcher disclosed herein primarily lies in
the geometry and functionality of the pulley drivers, which may
comprise axially aligned, counter opposed compression springs.
These springs may be compressed via the rotation of a pair of
spring compression cam pulleys, rotationally opposed and axially
fixed to a larger drive cam pulley. Thus, as the drive cable is
drawn from the drive cam pulleys, the spring compression cam
pulley, slaved to each other, may retract the spring compression
cable, and may squeeze or compress the compression springs to store
energy, which may be released as the drive cable is allowed to
retract. This arrangement may utilize the compression spring axis,
drive cable, and spring compression cable in parallel, resulting
with counter opposing momentums and pure linear force on the
compression springs and supporting assembly. This arrangement may
also isolate the high force, strength area to a small portion of
the launcher as opposed to the entire length of the launcher.
In various embodiments, the launcher may regulate tension through
leverage ratios between cams (e.g., lobed cams), such as those
found in recreational compound archery bows where energy is stored
through elastic limb deflection. Because scaling a compound bow
with use of a UAV may prove impractical due to size and material
property limitations, it may be preferred to utilize compression
springs in conjunction with cam tension. As a result, cam tension
in lieu of limb deflection may allow sufficient energy storage and
constant force regulation.
In the accompanying drawings, like reference numbers generally
indicate like elements. Reference character 535 and variations
thereof such as, for example, 535a, 535b, 535c, 535d, 535e, 535f,
535g, and 535h, are used to depict embodiments (i.e., carriage
wheels). Several views are presented to depict some, though not
all, of the possible orientations of the embodiments of the
launcher.
FIG. 1 is an illustration of an exploded, perspective view of one
embodiment of a launcher for an unmanned aircraft. As shown in FIG.
1, one embodiment of the launcher 100 may comprise: a launch rail
105, carriage 110, pulley drivers 115, 215, and a cable and pulley
system. As discussed above, the launch rail 105 may be one or more
bars, rails, or beams serving as a structure or frame for guiding
the unmanned aircraft or UAV during launching. In various
embodiments, the launch rail 105 may be constructed as a single
rail or beam or may be constructed of a plurality of rails or
beams. For example, as shown in FIG. 1, one embodiment of the
launch rail 105 may comprise two support beams joined and disposed
in parallel, such that a track 101 is formed or created in-between
the two beams. This track 101 may traverse along the length of the
launch rail 105 and may be configured for the carriage 110 to
engage thereon, such that the carriage 110 may slide and accelerate
along the track 101 linearly.
In various embodiments, the launch rail 105 may be segmented, such
that the launch rail 105 may be folded or disassembled for storage
or transport. For example, as shown in FIGS. 10A to 10C, one
embodiment of the launch rail 105 may comprise two segments--i.e.,
a forward beam portion 420 and an aft beam portion 470. The forward
beam portion 420 may be coupled to the aft beam portion 470 via a
hinge or pivot, thereby allowing the forward beam portion 420 to
impart hinge or pivot movement via folding or collapsing.
Alternatively, in another embodiment, the launch rail 105 may be
one or more non-segmented bars, rails, or beams, which prevents
folding or disassembling of the launch rail 105.
In various embodiments, the length of the launch rail 105 may also
vary, depending upon the distance required to achieve the desired
launch velocity. This launch velocity preferably does not exceed
the acceleration threshold of the unmanned aircraft, as well as the
distance required to stop or arrest the carriage 110. For example,
in various embodiments, the length of the launch rail 105 may
extend between approximately 50 to 150 inches. In another
embodiment, the length of the launch rail 105 may be approximately
100 inches. In alternative embodiments, the length of the launch
rail 105, however, may be less than 50 inches or may extend beyond
150 inches.
FIG. 1 also shows that the launch rail 105 may comprise a leg 106,
which may be adapted to removeably couple or attach to the distal
end of the launch rail 105. The leg 106 may provide additional
support to the launcher 100 and may create an incline for launching
the unmanned aircraft. In some embodiments, the leg 106 may be
coupled to the distal end of the launch rail 105 via a hinge to
allow various degrees of incline. Alternatively, the leg 106 may
also be attachable to the launch rail 105 and removable. Although
FIG. 1 depicts the launcher 100 having a single leg, various
embodiments of the launcher 100 may comprise multiple legs such as
two legs or three legs.
In various embodiments, the leg 106 may be configured to mount onto
a vehicle or vessel (e.g., truck, boat, ship). Alternatively, the
leg 106 may also be configured to mount onto a fixed platform
(e.g., building). For example, as shown in FIGS. 11A and 11B,
another embodiment of the launcher 1000 may comprise a leg 1060
coupled to a platform of a ship or vessel.
Additionally, FIG. 1 shows that the launcher 100 may comprise a
winch 169, which may be any mechanical device that is used to pull
in (wind up) or let out (wind out) or otherwise adjust the tension
of a rope, cable, or belt. The winch 169 may comprise a winch drum
168 and winch cable 167 (shown in FIGS. 8A to 8F), wherein the
winch cable 167 may be windable on the winch drum 168. In various
embodiments, the winch 169 may operate automatically (e.g., via a
motor) or manually (e.g., via crank and hand). For example, in one
embodiment, the winch 169 may be electrically powered for automatic
winding of the winch cable 167.
FIG. 1 also shows that the launcher 100 may comprise a carriage
110, which may be any support structure for holding, supporting,
and/or releasing the unmanned aircraft for launch or takeoff. In
various embodiments, the carriage 110 may be adapted to engage with
the track 101 of the launch rail 105 and may be adapted to move or
slide linearly along the track 101. In one embodiment, the carriage
110 may comprise a carriage body 505, an arm support shaft 521, and
carriage arms 510, 511, which may be pivotally or rotatably coupled
to the arm support shaft 521 of the carriage body 505. The carriage
arms 510, 511 may also be adapted to contact and grip the unmanned
aircraft in order to provide support to the unmanned aircraft
during takeoff. In order for the carriage 110 to move, translate,
or slide linearly along the track 101, the carriage 110 may utilize
carriage wheels 535a, 535b, 535c, 535d, 535e, 535f, 535g, 535h
(shown in FIG. 5), all of which may be movably engaged within the
internal cavity or sides of the launch rail 105.
Importantly, FIG. 1 shows that the launcher 100 may comprise pulley
drivers 115, 215, which may be configured to generate pulley drive
forces that drive or move the slider assemblies 120, 220 along a
predetermined path. Specifically, these pulley drive forces may be
generated via biasing of the compression springs 175, 176, 177,
178, 275, 276, 277, 278, and the biasing may move the slider
assemblies 120, 220 along the length of one or more linear bearing
shafts 170, 171, 270, 271 (shown in FIGS. 2A and 2B). The length of
the linear bearing shafts 170, 171, 270, 271 may be dependent upon
the length of the pulley drivers 115, 215, as the linear bearing
shafts 170, 171, 270, 271 may traverse along the longitudinal body
of each pulley driver 115, 215. For example, in various
embodiments, the length of each pulley driver 115, 215 may extend
between approximately 20 to 60 inches. In another embodiment, the
length of a pulley driver 115, 215 may be approximately 40 inches.
In alternative embodiments, the length of the pulley driver 115,
215, however, may be less than 20 inches or may extend beyond 60
inches.
In one embodiment, the pulley drive forces created by the pulley
drivers 115, 215 may be converted into a single launching force
(via a cable and pulley system) that drives the carriage 110 along
the launch rail 105. Specifically, the pulley drive forces applied
to the slider assemblies 120, 220 may actuate the drive cables and,
in turn, may drive the carriage 110 along the launch rail 105.
Additionally, in various embodiments, the pulley drivers 115, 215,
which may be hingedly coupled to a proximal end of the launch rail
105, may be oriented in an orthogonal manner with respect to the
launch rail 105, such that the pulley drivers 115, 215 may be
oriented away from each other. In this manner, the pulley drivers
115, 215 may generate pulley drive forces in opposing directions
relative to each other in order for the slider assemblies 120, 220
to move away from each other. As a result, pulley drive forces
applied to the slider assemblies 120, 220 can drive the cable and
pulley system, which in turn, drives the carriage 110 along the
launch rail 105.
In various embodiments, the force generated by each pulley driver
115, 215 may vary. For instance, the maximum force generated by one
embodiment of the compression spring 175, 176, 177, 178, 275, 276,
277, 278 for each pulley driver 115, 215 may be approximately 6,500
lbf, whereas the maximum force generated by another embodiment of
the compression spring 175, 176, 177, 178, 275, 276, 277, 278 for
both pulley drivers 115, 215 may be about 13,000 lbf.
In various embodiments, the tension force for the drive cables and
spring compression cable may also vary. For instance, the tension
force of some embodiments of the first drive cable 165 may vary
between approximately 860-1270 lbf, whereas the tension force of
various embodiments of the second drive cable 166 may be between
approximately 430-635 lbf. In some embodiments, the tension force
in the spring compression cable 805 may be between approximately
960-5204 lbf.
When launching the unmanned aircraft, the maximum force generated
by various embodiments of the compression springs 175, 176, 177,
178, 275, 276, 277, 278 for each pulley driver 115, 215 may be
approximately 2,500 lbf, whereas the maximum force generated by
other embodiments of the compression spring 175, 176, 177, 178,
275, 276, 277, 278 for both pulley drivers 115, 215 may be about
5,000 lbf. Additionally, the tension force in the first drive cable
165 may be approximately 11,300 lbf. Additionally, in several
embodiments, the tension force in the second drive cable 166 may be
approximately 5700 lbf. In some embodiments, the tension force in
the spring compression cable 805 may be approximately 5204 lbf.
As discussed above, the launcher 100 may also comprise a cable and
pulley system for converting the opposing pulley drive forces into
a single launching force for driving the carriage 110 for launch.
In various embodiments, the cable and pulley system may be
operatively associated with the pulley drivers 115, 215 and
carriage 110 and may comprise: launch rail forward pulleys 125,
130, launch rail aft pulleys 135, 140, a pulley block 145, a winch
cable interface 150 (shown in FIGS. 8A to 8F), a centering pulley
sheave 155 (shown in FIG. 5), drive cam pulleys 160, 260, a first
drive cable 165 (shown in FIGS. 8A to 8F), and a second drive cable
166 (shown in FIGS. 7A to 7F). The launch rail forward pulleys 125,
130 may be mounted alongside each other and may be located near or
at the distal end of the launch rail 105. On the other hand, the
launch rail aft pulleys 135, 140, which may also be mounted
alongside each other, may be located near the proximal end of the
launch rail 105 and preferably beneath the launch rail 105. This
may allow the first drive cable 165 and second drive cable 166,
both being operatively coupled to each other, to traverse or extend
from the proximal end of the launch rail 105 to the distal end of
the launch rail 105--i.e., from the launch rail aft pulleys 135,
140 to the launch rail forward pulleys 125, 130.
In one embodiment, the pulley block 145 may be positioned beneath
the launch rail 105 and may be moveably engaged with the underside
of the launch rail 105. This may allow the pulley block 145 to
translate, move, or slide along the underside or bottom portion of
the launch rail 105. Importantly, the pulley block 145 may comprise
a pair of pulley block pulleys 825, 830 (shown in FIGS. 8A to 8F)
and a centering pulley block pulley 835, all of which may be used
for reeving either the first drive cable 165 or second drive cable
166. In one embodiment, the pulley block pulleys 825, 830 may be
mounted alongside each other and the centering pulley block pulley
835 may be mounted near or at the centerline on the pulley block
145.
Similarly, like the pulley block 145, the winch cable interface 150
may also be positioned beneath the launch rail 105 and may be
adapted to slide along the underside of the launch rail 105. The
winch cable interface 150 may also be disposed between the pulley
block 145 and launch rail forward pulleys 125, 130, such that the
winch cable interface 150 may interact with the winch 169 rather
than the pulley block 145.
The cable and pulley system may also comprise a centering pulley
sheave 155 and drive cam pulleys 160, 260. In various embodiments,
the centering pulley sheave 155 may be coupled to the carriage body
505 as multiple pieces or may be integrated into the carriage body
505 as a single piece. The centering pulley sheave 155 may embody a
grooved wheel (or a portion thereof) for holding or reeving a rope,
belt, cable, or the like (i.e., second drive cable 166). In this
manner, the rope, belt, or cable may move freely around the
carriage 110, while minimizing wear and abrasion on cable or belt.
Regarding the drive cam pulleys 160, 260, each drive cam pulley
160, 260 may be rotatably coupled to a corresponding main shaft
330, 380 (shown in FIGS. 3A and 3B) located within each slider
assembly 120, 220 and may be configured to rotate around an axis
defined by the main shaft 330, 380. In various embodiments, the
relative shape of the drive cam pulleys 160, 260 may also be lobed,
such that the thrust imparted to the carriage 110 and unmanned
aircraft may remain at lease relatively constant.
The cable and pulley system may also comprise a first drive cable
165 and a second drive cable 166. The first drive cable 165 may be
operatively associated with the pulley drivers 115, 215 and may
extend along the lower, proximal end portion of the launch rail
105. In particular, each of the opposing ends of the first drive
cable 165 may be coupled or attached to an associated drive cam
pulley 160, 260, and from there, may extend towards the proximal
end of the launcher 100 around the launch rail aft pulleys 135,
140. A center or intermediate portion of the first drive cable 165
may also be reeved around the centering pulley block pulley 835
located on the pulley block 145, such that the first drive cable
165 extends from the slider assemblies 120, 220 within the pulley
drivers 115, 215, towards the proximal end of the launcher 100 via
the launch rail aft pulleys 135, 140, and around the centering
pulley block pulley 835. This configuration may allow the pulley
drivers 115, 215 to drive the pulley block 145 via the pulley drive
forces.
Regarding the second drive cable 166, this cable may be operatively
associated with the pulley block 145 and carriage 110, and may
extend towards the distal end portion of the launch rail 105.
Specifically, each opposing end of the second drive cable 166 may
be coupled or attached to the winch cable interface 150, and from
there, may extend around an associated pulley block pulley 825, 830
and towards the launch rail forward pulleys 125, 130 located at the
distal end of the launch rail 105. The second drive cable 166 may
also have a center or intermediate portion that may be reeved
around the centering pulley sheave 155 located on the carriage 110.
Thus, in one embodiment, the second drive cable 166 may extend
from: (1) the winch cable interface 150, (2) pulley block 145 (via
the pulley block pulleys 825, 830), (3) distal end of the launch
rail 105 (via the launch rail forward pulleys 125, 130), and (4)
carriage 110. As such, any movement of the pulley block 145 with a
tensioned or taut second drive cable 166 may affect movement of the
carriage 110 along the launch rail 105.
As discussed above, the cable and pulley system may also comprise a
winch 169 mounted at the distal end of the launch rail 105. The
winch 169 may comprise a winch drum 168 and a winch cable 167
windable on the winch drum 168. In a preferred embodiment, the
winch cable 167 may be coupled or attached to the winch cable
interface 150, such that any pulling or retracting of the winch
cable 167 by the winch 169 may result with movement of the winch
cable interface 150 and pulley block 145.
In the event of device failure of the winch 169, various
embodiments of the launcher 100 may also comprise a second winch
455, which may be used as a manual back-up winch. Specifically, in
the event winch 169 fails to release or unwind, the second winch
455 may be used to safely release any energy stored in the
compression springs 175, 176, 177, 178, 275, 276, 277, 278. The
second winch 455 may comprise a winch drum 454, a winch cable 453,
and a quick release fastener 469, for pulling or retracting the
carriage 110 backwards or rearwards. The second winch 455 may also
be configured to wind the winch cable 453 automatically (e.g., via
motor) or manually (via, crank and hand). In a preferred
embodiment, the second winch 455 may be worm gear driven winch.
FIGS. 2A and 2B are illustrations of exploded, side views of some
embodiments of the pulley drivers. Specifically, FIG. 2A depicts
one embodiment of the left pulley driver 115, whereas FIG. 2B
depicts one embodiment of the right pulley driver 215, both of
which may couple to the proximal end of the launch rail 105. As
shown in FIGS. 2A and 2B, embodiments of the pulley drivers 115,
215 may comprise: compression springs 175, 176, 177, 178, 275, 276,
277, 278, slider assemblies 120, 220, linear bearing shafts 170,
171, 270, 271, spring couplers 180, 181, 280, 281, upper c-channels
183, 283, lower c-channels 184, 284, end plates 185, 285, center
block interfaces 190, 290, adjustable leveling mounts 192, 292, and
pulley driver wheels 195, 295.
The compression springs 175, 176, 177, 178, 275, 276, 277, 278 may
be any flexible and elastic biasing member that applies an elastic
biasing force to the slider assemblies 120, 220 in a sliding
direction. In particular, compression springs 175, 176 (which may
be coupled to compression springs 177, 178 via spring couplers 180,
181, respectively) may apply a biasing force to slider assembly 120
in order to move or translate slider assembly 120 along linear
bearing shafts 170, 171. This may cause slider assembly 120 to move
in a direction towards end plate 185. Similarly, compression
springs 275, 276 (which may be coupled to compression springs 277,
278 via spring couplers 280, 281, respectively) may also apply a
biasing force to slider assembly 220 in order to move or translate
slider assembly 220 along linear bearing shafts 270, 271. This may
also cause slider assembly 220 to move in a direction towards end
plate 285. Given that pulley drivers 115, 215 may be oriented away
from each other and may be adapted to produce a pair of opposing
pulley drive forces, the slider assemblies 120, 220 may move or
slide in opposing directions relative to each other. The pulley
drivers 115, 215 may also be oriented away from each other, as the
center block interfaces 190, 290 of the pulley drivers 115, 215 may
be moveably attached to the center block 460 of the launch rail
105.
FIGS. 2A and 2B also show how upper c-channels 183, 283, lower
c-channels 184, 284, end plates 185, 285, and center block
interfaces 190, 290 together may form the housing for the inner
components of the pulley drivers 115, 215. FIG. 2A, for example,
shows that upper c-channel 183, lower c-channel 184, end plate 185,
and center block interface 190 together may house or contain
compression springs 175, 176, 177, 178, linear bearing shafts 170,
171, spring couplers 180, 181, and slider assembly 120 of the left
pulley driver 115. Similarly, FIG. 2B shows that upper c-channel
283, lower c-channel 284, end plate 285, and center block interface
290 together may also house compression springs 275, 276, 277, 278,
linear bearing shafts 270, 271, spring couplers 280, 281, and
slider assembly 220 of the right pulley driver 215.
FIGS. 2A and 2B also show that, in some embodiments, the pulley
drivers 115, 215, each may comprise adjustable leveling mounts 192,
292 for securing or leveling the launcher 100 when the launcher 100
is in a launch configuration. The adjustable leveling mounts 192,
292 may be movably attached to end plates 185, 285 and may be used
to adjust an incline or height of the pulley drivers 115, 215.
Pulley driver wheels 195, 295 may also be axially fixed to the
lower c-channels 184, 284 for ease of transportation of the
launcher 100 when the launcher 100 is in a stowed
configuration.
FIGS. 3A and 3B are illustrations of exploded, perspective views of
some embodiments of the slider assemblies. Specifically, FIG. 3A
depicts one embodiment of a left slider assembly 120 for the left
pulley driver 115, whereas FIG. 3B depicts one embodiment of a
right slider assembly 220 for the right pulley driver 215. As shown
in FIGS. 3A and 3B, embodiments of the slider assemblies 120, 220
may comprise: drive cam pulleys 160, 260, spring compression cam
pulleys 310, 360, ball bearings 315, 316, 365, 366, flanged linear
bearings 320, 321, 370, 371, spring perches 325, 326, 375, 376,
slider blocks 335, 336, 385, 386, and main shafts 330, 380. The
drive cam pulleys 160, 260 may be any rotating piece in a
mechanical linkage used for transforming rotary motion into linear
motion and vice versa. The overall shape of the drive cam pulleys
160, 260 may vary, depending on the type of launcher 100, and may
affect the acceleration of the launching for the carriage 110.
Importantly, each drive cam pulley 160, 260 may be attached to the
opposing ends of the first drive cable 165 in order to impart
rotational movement on the drive cam pulleys 160, 260. Thus, when
the first drive cable 165 is pulled and tensioned, the drive cam
pulleys 160, 260 may rotate around an axis defined by the main
shafts 330, 380.
In addition to the drive cam pulleys 160, 260, the slider
assemblies 120, 220 may also comprise spring compression cam
pulleys 310, 360, which may be axially fixed to an associated drive
cam pulley 160, 260. Like the drive cam pulleys 160, 260, the
spring compression cam pulleys 310, 360 may be rotatable along an
axis defined by the main shafts 330, 380, which may allow the drive
cam pulleys 160, 260 to likewise impart rotational movement to the
spring compression cam pulleys 310, 360 in the event the drive cam
pulleys 160, 260 are pulled or rotated by the first drive cable
165. Thus, as each slider assembly 120, 220 moves along their
respective linear bearing shafts 170, 171, 270, 271, the drive cam
pulleys 160, 260 and spring compression cam pulleys 310, 360 may
also axially rotate around an associated main shaft 330, 380.
In one embodiment, each opposing end of the spring compression
cable 805 (shown in FIGS. 8A to 8F) may be attached or coupled to a
respective spring compression cam pulley 160, 260. In this manner,
the slider assemblies 120, 220 may pull towards each other upon
rotation of the spring compression cam pulleys 310, 360. In
particular, when the spring compression cam pulleys 310, 360 rotate
due to the rotation of the drive cam pulleys 160, 260, the spring
compression cable 805 may be tensioned or taut. As a result, the
slider assemblies 120, 220 may pull towards each other as the
spring compression cable 805 becomes winded around the slider
assemblies 120, 220.
To help further facilitate rotational movement of the drive cam
pulleys 160, 260 and spring compression cam pulleys 310, 360, ball
bearings 315, 316, 365, 366 may also be axially coupled to the main
shafts 330, 380 to reduce rotational friction and to support any
radial and axial loads. In various embodiments, the ball bearings
315, 316, 365, 366 may have a diameter that engages with or may be
flushed with the openings of the inner diameter of the cam pulleys
310, 360 and/or spring compression cam pulley 160, 260. Also, in
various embodiments, the ball bearings 315, 316, 365, 366 may also
utilize at least two races to in order to contain the balls and
transmit loads through the balls.
FIGS. 3A and 3B also show that the slider assemblies 120, 220 may
utilize slider blocks 335, 336, 385, 386 configured to slide or
translate along the linear bearing shafts 170, 171, 270, 271.
Specifically, a portion of each slider block 335, 336, 385, 386 may
comprise a main shaft opening 335a, 336a, 385a, 386a configured to
attach to an opposing end of a main shaft 330, 380. Another portion
of each slider block 335, 336, 385, 386 may also comprise a flanged
linear bearing opening 335b, 336b, 385b, 386b adapted to engage
with an axial portion of a flanged linear bearing 320, 321, 370,
371. The flanged linear bearings 320, 321, 370, 371 in conjunction
with spring perches 325, 326, 375, 376 may engage and slide with
the linear bearing shafts 170, 171, 270, 271 in order to facilitate
sliding of the slider assemblies 120, 220 along the linear bearing
shafts 170, 171, 270, 271. Thus, in addition to the drive cam
pulleys 160, 260 and spring compression cam pulleys 310, 360
rotating around the main shafts 330, 380, the slider assemblies
120, 220 may also slide linearly along the linear bearing shafts
170, 171, 270, 271. As such, various embodiments of the slider
assemblies 120, 220 may impart rotational movement as well as
linear movement.
As discussed above, each slider assembly 120, 220 may be adapted to
move, slide, or translate in a direction along predetermined paths
(i.e., based on the orientation of the linear bearing shafts 170,
171, 270, 271). These predetermined paths may be oriented away from
each other, thereby causing the slider assemblies 120, 220 to slide
away from one another. Thus, as the slider assemblies 120, 220
slide along the linear bearing shafts 170, 171, 270, 271, the first
drive cable 165 and spring compression cable 805 may be taut,
thereby causing rotation on the drive cam pulleys 160, 260 and
spring compression cam pulleys 310, 360. For example, in one
embodiment, when the second drive cable 166 is pulled or retracted
by the winch 169, the first drive cable 165 may also be pulled,
thereby imparting rotation of the drive cam pulleys 160, 260 along
the main shafts 330, 380. In this manner, the spring compression
cable 805, which may be coupled to the spring compression cam
pulleys 310, 360 of the slider assemblies 120, 220, may also remain
taut, thereby causing the spring compression cable 805 to wind
around the spring compression cam pulleys 310, 360. As a result,
the slider assemblies 120, 220 may rotate and translate towards
each other. A more detailed explanation of the operation of the
slider assemblies 120, 220 is described in FIGS. 7A through 7F and
FIGS. 8A through 8F below.
FIG. 4 is an illustration of an exploded, perspective view of one
embodiment of the launch rail. As shown in FIG. 4, one embodiment
of the launch rail 105 may comprise a forward launch rail assembly
400 and an aft launch rail assembly 450, wherein the forward launch
rail assembly 400 may be hingedly coupled to the aft launch rail
assembly 450 via a moveable joint or hinge. In this manner, the
forward launch rail assembly 400 may swing, move, or fold onto the
aft launch rail assembly 450 about a fixed axis of rotation,
thereby allowing the launch rail 105 to be folded into a stowed
configuration for storage or transport.
FIG. 4 shows that one embodiment of the forward launch rail
assembly 400 may also comprise: a winch 169, forward pulley support
410, launch rail forward pulleys 125, 130, forward beam portion
420, brake pulley support assembly 425, quick release pin 430,
forward hinges 432, 433, and main cable retention pins 435. As
discussed above, the winch 169 may be any device that winds or
otherwise adjust the tension of a rope, cable, or belt. The winch
169 may comprise a winch drum 168 and winch cable 167 that is
windable on the winch drum 168. The winch cable 168 may also be
wounded automatically (via a motor) or manually (via hand). In one
embodiment, the winch 169 may be electrically powered for automatic
winding of the winch cable 167.
The launch rail forward pulleys 125, 130 may be any grooved wheel
or a portion thereof, designed to support movement and change of
direction of the second drive cable 166 (preferably when taut or
tensioned) along the groove wheel portion of the launch rail
forward pulleys 125, 130. The launch rail forward pulleys 125, 130
may be mounted near or at the distal end of the launch rail 105 and
may be mounted alongside each other via the forward pulley support
410.
The brake pulley support assembly 425 may be a device used to
decelerate or halt the carriage 110 after launch or takeoff of the
unmanned aircraft. Thus, as the carriage 110 reaches the brake
pulley support assembly 425, the carriage 110 may decelerate or
perform a stop. The brake pulley support assembly 425 may be
mounted at the distal end of the forward beam portion 420 of the
launch rail 105, as shown on FIG. 1, and may comprise: brake pulley
supports 440, 441, and brake pulleys 444, 445, 446, 447. The brake
pulley supports 440, 441 may be adapted to hold and secure the
brake pulleys 444, 445, 446, 447 on the forward beam portion 420 of
the launch rail 105. The brake pulleys 444, 445, 446, 447, on the
other hand, may be used to guide, support, and direct a portion of
the second drive cable 166 from the launch rail forward pulleys
125, 130 and along the length of the launch rail 105. For example,
in one embodiment, the second drive cable 166 may extend between
brake pulley 444 and brake pulley 445 and then around a portion of
brake pulleys 446, 447, as shown in FIGS. 7A to 7F. In an
alternative embodiment, the second drive cable 166 may extend
around a portion of the outer circumference of brake pulleys 444,
445 and then between brake pulley 446 and brake pulley 447.
Importantly, the brake pulleys 444, 445, 446, 447 may be positioned
along the brake pulley support assembly 425 and launch rail 105 in
order to intercept the carriage 110 after takeoff. In this manner,
the brake pulleys 444, 445, 446, 447 may decelerate and arrest the
carriage 110 into a stop by restricting the second drive cable 166
once the carriage 110 slides past the brake pulley support assembly
425.
FIG. 4 also shows that the forward launch rail assembly 400 may
also comprise a quick release pin 430, forward hinges 432, 433, and
main cable retention pins 435. As discussed above, the top portions
of the forward hinges 432, 433 and aft hinges 480, 481 may be
hingedly coupled, such that the forward beam portion 420 may fold
onto the aft beam portion 470. Thus, when the launch rail 105 is
not folded (i.e., the forward beam portion 420 is open and extended
from the aft beam portion 470), a quick release pin 430 may be
inserted into the bottom portions of the forward hinges 432, 433
and aft hinges 480, 481 in order to lock the launch rail 105 into
an unfolded position. In this manner, the launch rail 105 may
remain open and extended and may help prevent the launch rail 105
from folding or collapsing during launch or take off. In various
embodiments, cable retention pins 435 may also be used to help
secure or guide the second drive cable 166 onto the launch rail
105.
FIG. 4 also shows that the launch rail 105 may also comprise an aft
launch rail assembly 450, which may further comprise: a second
winch 455, center block 460, launch rail aft pulleys 135, 140, aft
beam portion 470, forward beam wheels axle support 475, aft hinges
480, 481, and linear bearing shafts 485, 486. As discussed above,
the second winch 455 may be used to help facilitate winding of the
winch cable 453 in order to pull the carriage 110 rearwards and may
comprise a winch drum 454, winch cable 453, and a quick release
fastener 469. The second winch 455 may also serve as a backup winch
in the event of device failure of the other winch 169.
The center block 460 may be a junction used for attaching the
pulley drivers 115, 215 onto the proximal or rear end of the launch
rail 105. Specifically, in one embodiment, the distal end of the
center block 460 may attach onto the distal end of the aft beam
portion 470. The proximal end of the center block 460, on the other
hand, may hingedly couple both pulley drivers 115, 215, such that
the first ends of the pulley drivers 115, 215 may be adjacent to
one another.
The forward beam wheels axle support 475 may be an axle or shaft
for attaching forward beam wheels 395, 495 (shown in FIGS. 10A to
10B) when the launcher 100 is in a stowed configuration. The aft
hinges 480, 481, as discussed above, may be configured to hingedly
couple to the forward hinges 432, 433 of the forward launch rail
assembly 400. The linear bearing shafts 485, 486 may be used to
guide the pulley block 145 linearly when moving along the launch
rail 105 and may comprise linear bearing shaft supports 490, 491,
492, 493. The linear bearing shafts 485, 486 may also provide extra
support for the aft beam portion 470 to help offset any torsional
misalignment on the launch rail 105.
FIG. 5 is an illustration of an exploded, perspective view of one
embodiment of the carriage. As shown in FIG. 5, one embodiment of
the carriage 110 may comprise: a carriage body 505 and carriage
arms 510, 511. As discussed above, the carriage 110 may be designed
to support and/or cradle a UAV that is to be launched. The carriage
110 may also be adapted to travel linearly on the launch rail 105.
In order to facilitate such movement, the carriage body 505 may
utilize a plurality of carriage wheels 535a, 535b, 535c, 535d,
535e, 535f, 535g, 535h, all of which may be adapted to rollably
engage within the internal sides of the launch rail 105, such that
the carriage body 505 is engaged with the track 101 of the launch
rail 105. In various embodiments, skid blocks 540a, 540b, 540c,
540d may also be used to help facilitate movement of the carriage
110 along the track of the launch rail 105.
FIG. 5 also shows that the carriage body 505 may comprise a
centering pulley sheave 155 and an attachment point 541. The
centering pulley sheave 155 may be a grooved wheel or a portion
thereof for holding a rope, belt, cable, or the like. This allows
the rope, belt, or cable to move freely around the carriage 110,
while minimizing wear and abrasion on the cable. In one embodiment,
the centering pulley sheave 155 may be a simple eye or center
opening used to insert the second drive cable 166, so that the
second drive cable 166 may be coupled to the carriage body 505. In
another embodiment, the centering pulley sheave 155 may be a
separate piece with a center opening that is coupled or attached to
the carriage body 505.
FIG. 5 also depicts an attachment point 541 that may be located at
the proximal end of the carriage body 505 for pulling or retracting
the carriage 110 for launch. Specifically, the attachment point 541
may be used for attaching a quick release fastener 469 coupled to a
second winch 455 for pulling or retracting the carriage 110
rearwards for launching. In one embodiment, the attachment point
541 may comprise a curved shaft for easy engagement and release of
the carriage 110 for launch.
Importantly, FIG. 5 shows that the carriage 110 may also comprise
carriage arms 510, 511, which may be rotatably coupled to the arm
support shaft 521 of the carriage body 505. As discussed above, the
carriage arms 510, 511 may be configured to support the unmanned
aircraft that is to be launched and may rotate forward and
outwardly after takeoff in order to release the aircraft. In
various embodiments, the carriage arms 510, 511 may comprise edge
contacts 515, 516, 517, 518, 519, 520 constructed of any flexible
or pliable material such as a polymer, foam, or rubber. This may
allow the carriage arms 510, 511 to contact the unmanned aircraft
without scratching or denting. Tensioned cables, such as guy wires
525 may also be used to minimize the inward force from crushing the
fuselage of the unmanned aircraft, as the guy wire 525 may be used
to support a majority of the force. The cable length and amount of
stretch of the guy wire 525 may also be used for determining the
desired amount of force on the fuselage. The guy wire 525 may be
coupled between the carriage arms 510, 511 and guy wire support
shaft 530 and may be tensioned or taut when the carriage arms 510,
511 are in an upright position
The edge contacts 515, 516, 517, 518, 519, 520 of each carriage arm
510, 511 may also have a curved shape, so as to conform to the
shape of the fuselage of the unmanned aircraft. Using these edge
contacts 515, 516, 517, 518, 519, 520, the carriage 110 may
securely grip the unmanned aircraft during launch and may quickly
release the unmanned aircraft at the end of launch sequence.
Importantly, due to the availability of structural hard points on
the unmanned aircraft capable of supporting the high launch load,
the carriage 100 may interface the unmanned aircraft at certain
structural hard points such as the base of the wings. As a result,
various embodiments of the carriage arms 510, 511 may rotate around
a pivot axis, and that axis may be canted outwardly away from a
vertical plane. In this manner, the carriage arms 510, 511 may
rotate outwardly for launch.
As discussed above, one embodiment of the carriage arms 510, 511
may rotate around a pivot axis, and that axis may be canted
outwardly away from a vertical plane. In this manner, the carriage
arms 510, 511 may rotate outwardly for launch. For example, in one
embodiment, the arms may pivot around an axis of approximately
45.degree., allowing the ends of the carriage arms 510, 511 to move
down and away from the aircraft when rotated. Thus, when the
carriage 110 decelerates during launch or takeoff, the forward
momentum of the carriage arms 510, 511 may cause the carriage arms
510, 511 to fling open via pivoting around the pivot axis. As the
carriage arms 510, 511 begin to open, the carriage arms 510, 511
may thus pivot downwardly and outwardly away in order to avoid
collision with the propeller or unmanned aircraft.
FIG. 6 is a flow diagram of one embodiment of a method for a launch
sequence of the launcher. As shown in FIG. 6, one embodiment of the
method 600 may comprise steps: 605, 610, 615, 620, 625, 630, 635,
640, 645, 650, 655, 660, 665, 670, 675, and 680. Before beginning
step 605, an unmanned aircraft may be installed on the carriage
110. This may be accomplished by having the carriage arms 510, 511
of the carriage 110 engage with the fuselage of the unmanned
aircraft. For example, in one implementation, the underside or base
portion of the wings of the unmanned aircraft may be rested on top
of the carriage arms 510, 511, whereas the body of the unmanned
aircraft may be gripped and secured in-between the inner side
portions of the carriage arms 510, 511. In this arrangement, the
unmanned aircraft may be released upon forward rotation of the
carriage arms 510, 511 during launch.
Once the unmanned aircraft is installed on the carriage 110 of the
launcher 100, step 605 may be performed. Here, the user may
energize the winch 169 and may cause the winch drum 168 to actuate
and retract the winch cable 167. As discussed above, the winch
cable 167 may be coupled to the distal end of the winch interface
150, while the opposing ends of the second drive cable 166 may be
both directly attached to the proximal end of the winch interface
150. As a result, the winch 169 may also retract and pull the
second drive cable 166 in the event the winch 169 is actuated.
Importantly, portions of the second drive cable 166 may extend
around the pulley block pulleys 825, 830 located on the pulley
block 145. This may allow the winch 169 to pull or move the pulley
block 145 forward, as shown in step 610. Thus, upon retraction of
the winch cable 167 and winch cable interface 150 by the winch 169,
the pulley block 145 may also be retracted or pulled forward.
As discussed above, a centering pulley block pulley 835 may also be
mounted near or at the centerline on the pulley block 145 and may
be used for reeving the first drive cable 165. Thus, when the winch
169 retracts or pulls the second drive cable 166 in step 605, the
winch 169 may also be pulling or retracting the first drive cable
165. Given that the first drive cable 165 may be winded around the
drive cam pulleys 160, 260, any retraction or pulling of the second
drive cable 166 may further result with the unwinding of the first
drive cable 165 from the drive cam pulleys 160, 260, shown in step
615. Thus, the drive cam pulleys 160, 260 may rotate, which in
turn, may also cause the spring compression cam pulleys 310, 360 to
also rotate, shown in steps 620 and 625, respectively.
In step 630, rotation created by spring compression cam pulleys
310, 360 may generate torque, thereby causing the spring
compression cable 805 to be tensioned and taut. As a result, the
spring compression cam pulleys 310, 360 may wind the spring
compression cable 805 and thus pull the slider assemblies 120, 220
towards each other. In this manner, the slider assemblies 120, 220
may slide towards the proximal end of the launch rail 105, as shown
in step 635. As the slider assemblies 120, 220 begin to slide or
translate towards each other, the slider assemblies 120, 220 may
also exert force upon the compression springs 175, 176, 177, 178,
275, 276, 277, 278, thereby compressing the compression springs
175, 176, 177, 178, 275, 276, 277, 278 and creating stored energy,
as shown in step 640. As such, the launcher 100 may be ready for
launch after the compression springs 175, 176, 177, 178, 275, 276,
277, 278 have been compressed.
In order to launch the unmanned aircraft, the carriage 110 may
launch or release the aircraft in step 650. Specifically, launching
of the carriage 110 may be performed simply by actuation of the
quick release fastener 469, which may be coupled to and release
from the attachment point 541 of the carriage 110. As discussed
above, the quick release fastener 469 may be tethered to a second
winch 455 via a second winch cable 453. Thus, upon release of the
carriage 110, the compression springs 175, 176, 177, 178, 275, 276,
277, 278 may expand, push, or bias the slider assemblies 120, 220
in a direction away from the center of the launcher 100, as shown
in step 655. The spring compression cable 805 may also unwind, and
any torque created by the spring compression cam pulleys 310, 360
may be transferred onto the drive cam pulleys 160, 260, shown in
steps 660 and 665. In this manner, the drive cam pulleys 160, 260
may also rotate in step 670 and retract the first drive cable 165,
thereby pulling the pulley block 145 rearward in step 675. As a
result, the pulley block 145 may also retract the second drive
cable 166, causing the carriage 110 to launch forward.
FIGS. 7A to 7F are illustrations of perspective views of one
embodiment of the launcher and shows the launcher in operation.
Additionally, FIGS. 8A through 8F are illustrations of bottom plan
views of the launcher 100 in operation, as depicted in FIGS. 7A
through 7F. As shown in FIGS. 7A to 7F and 8A to 8F, one embodiment
of the launcher 100 may comprise: a first drive cable 165 and
second drive cable 166. Each opposing end of the first drive cable
165 may be coupled to an associated drive cam pulley 160, 260, and
from there, extend around the launch rail aft pulleys 135, 140 and
reeved around the centering pulley block pulley 835. The second
drive cable 166, on the other hand, may have both opposing ends
coupled to the winch cable 167 via the winch cable interface 150,
and from there, may extend and be routed around the pulley block
pulleys 825, 830, launch rail forward pulleys 125, 130, brake
pulley support assembly 425, and carriage 110. FIG. 7A shows that
the carriage 110 may be fixed and stationary near the proximal end
of the launcher 100 via the quick release fastener 469.
Importantly, FIG. 7A shows the beginning of the loading sequence of
the launcher 100. Specifically, loading of the launcher 100 may
begin when the winch 169 is actuated and retracting both the winch
cable 167 and winch cable interface 150. This in turn may cause the
winch 169 to move the pulley block 145 forward. Given that both
ends of the second drive cable 166 may be coupled to the winch
cable 167 and routed around the pulley block pulleys 825, 830, any
movement by the pulley block 145 may also indirectly affect
movement of the first drive cable 165 via the second drive cable
166. For instance, FIGS. 7A and 8A show that, as the pulley block
145 moves forward, the first drive cable 165 may also be pulled
forward via the second drive cable 166. In this manner, the first
drive cable 165 may pull the slider assemblies 120, 220 inward and
rotate the drive cam pulleys 160, 260 inward. As a result, the
first drive cable 165 may payout, due to the rotation of the drive
cam pulleys 160, 260 and the translating movement of the slider
assemblies 120, 220. Each drive cam pulley 160, 260 may be axially
fixed to a respective spring compression cam pulley 310, 360 and
may be oppositely wrapped or winded. Thus, any unrolling of a drive
cam pulley 160, 260 may result with the winding of the spring
compression cable 805 and vice versa. As such, when the spring
compression cable 805 winds or rotates onto the spring compression
cam pulley 310, 360, the slider assemblies 120, 220 may be forced
to move or translate inwards against the opposing compression
springs 175, 176, 177, 178, 275, 276, 277, 278.
FIG. 8A shows the bottom plan view of one embodiment of the
launcher 100 in operation, as depicted in FIG. 7A and shows how the
first drive cable 165 and the second drive cable 166 may interface
each other at the pulley block 145. Specifically, FIG. 8A shows
that one embodiment of the pulley block 145 may comprise a pair of
pulley block pulleys 825, 830 and a centering pulley block pulley
835. Here, the centering pulley block pulley 835 may be disposed
near the bottom or proximal end of the pulley block 145, whereas
the pulley block pulleys 825, 830 may be disposed near the upper or
distal end of the pulley block 145. In this manner, the first drive
cable 165 may be reeved around the centering pulley block pulley
835 and opposing end portions of the second drive cable 166 may be
reeved around both pulley block pulleys 825, 830. As a result, a
2:1 ratio of force to displacement configuration may be
implemented, thereby allowing any force exerted by the first drive
cable 165 to result with approximately half the amount of force for
the second drive cable 166. Notably, this 2:1 cable configuration
may also result with a double displacement of the second drive
cable 166 with respect to the first drive cable 165 and may also
serve to create equilibrium in cable tension between the left and
right pulley drivers 115, 215.
FIG. 7B shows the slider assemblies 120, 220 sliding or translating
fully inward and the compression springs 175, 176, 177, 178, 275,
276, 277, 278 being fully or sufficiently compressed. As a result,
cable retraction by the winch 169 may terminate, resulting with the
winch cable 167 being fixed for the remainder of the launch
sequence. The launcher 100 may now be ready for launch upon
actuation of the quick release fastener 469 on the carriage 110. At
this time, the cumulative forces may be equal and opposite (e.g.,
forces exerted from the pulley block 145 of the launcher 100) and
the compression loads may be very high due to the compression of
the compression springs 175, 176, 177, 178, 275, 276, 277, 278.
FIG. 8B shows the bottom plan view of one embodiment of the
launcher 100 in operation, as depicted in FIG. 7B. Here, FIG. 8B
depicts the slider assemblies 120, 220 translating inwards towards
the launch rail 105. Thus, cable payout of the spring compression
cable 805 and first drive cable 165 may occur tangentially and
parallel to the pulley drivers 115, 215. This combination of the
drive cam pulleys 160, 260 and spring compression cam pulleys 310,
360 being axially fixed within the pulley drivers 115, 215 may
result with very little force acting orthogonal to the pulley
driver 115, 215, thereby allowing for minimal structure and lower
weight.
FIGS. 7C and 8C show the operation of the launcher when an unmanned
aircraft is being released by the carriage 110. Here, the slider
assemblies 120, 220 may move or translate outwards due to the
pulley drive forces generated by the pulley drivers 115, 215.
During this time, the drive cam pulleys 160, 260 may also rotate,
thereby winding the first drive cable 165. Because each of the
spring compression cam pulleys 310, 360 may be axially fixed with
the drive cam pulleys 160, 260, the winding of each of the drive
cam pulleys 160, 260 may result with the cable payout of the spring
compression cable 805 and winding of the first drive cable 165.
Thus, as the slider assemblies 120, 220 move or translate outwards
towards the opposing ends of the pulley drivers 115, 215, the
spring compression cable 805 may payout from the spring compression
cam pulleys 310, 360.
FIGS. 7D and 8D show the carriage 110 reaching the end of the
launch. Here, as the carriage 110 reaches the brake pulley support
assembly 425 and towards the distal end of the launch rail 105,
momentum may occur with the carriage 110 (i.e., carriage momentum),
pulley block 145, slider assemblies 120, 220, drive cam pulleys
160, 260, and spring compression cam pulleys 310, 360. The carriage
110, for example, may travel across the brake pulley support
assembly 425 via the momentum of the carriage. Upon crossing the
brake pulley support assembly 425, however, the carriage 110 may
move in a direction opposite to the rest of the other components of
the launcher 100. In particular, when the carriage 110 moves
forward on the track 101 and across the brake pulley support
assembly 425, other moving components of the launcher 100 may move
backwards or rearwards from the brake pulley support assembly 425.
For instance, a carriage 110 moving backwards or rearwards from the
brake pulley support assembly 425 may result with a pulley block
145 moving forward.
Importantly, as discussed above, the carriage arms 510, 511 may
rotate around a pivot axis and outwardly for launch. Thus, when the
carriage 110 decelerates, the forward momentum of the carriage arms
510, 511 may also cause the carriage arms 510, 511 to fling open
via pivoting around the pivot axis. In this manner, the carriage
arms 510, 511 may pivot downwardly and outwardly away, thereby
releasing the unmanned aircraft. This may also reduce the
likelihood of the carriage arms 510, 511 striking the unmanned
aircraft or launch rail 105.
Importantly, the carriage momentum may be higher than any momentum
generated by the launcher 100. This allows the carriage 110 to move
forward as well as overcome any inertia of the others components.
Thus, as the carriage 110 reaches a stop near the distal end of the
launch rail 105, the stored energy in the compression springs 175,
176, 177, 178, 275, 276, 277, 278 may pull the carriage 110
backwards or rearwards along the launch rail 105 and past the brake
pulley support assembly 425, thereby causing the carriage 110 to
oscillate across the brake pulley support assembly 425 until
frictional and inertial energy bring the carriage 110 to rest.
FIG. 7E shows the deceleration of the carriage 110 and FIG. 8E
shows the bottom plan view thereof. As the carriage 110 moves
forward across the brake pulley support assembly 425, the momentum
of other components moving in the opposite direction coupled with
the recompression of the pulley drivers 115, 215 may rapidly
decelerates the carriage 110. This deceleration may inertially
rotate and open the carriage arms 510, 511 and release the unmanned
aircraft or UAV. Once the carriage arms 510, 511 are completely
open or rotated, the carriage arms 510, 511 may be stopped in place
via a friction stop that is tightened by the rotation of the
carriage arms 510, 511.
FIG. 7F shows the carriage 110 decelerating and overshooting the
brake pulley support assembly 425 via recoil; FIG. 8F shows the
bottom plan view thereof. After the carriage 110 completely stops
in the forward direction and beyond the brake pulley support
assembly 425, the stored energy in the springs and the rest of the
launcher 100 may propel the carriage 110 backwards or rearwards
across the brake pulley support assembly 425. The carriage 100 may
then move back and forth across the brake pulley support assembly
425 several times, but may come to rest, as the inertial energy of
the carriage dissipates.
FIG. 9 is a flow diagram of one embodiment of a method for
converting the launcher from a stowed configuration to a launch
configuration. As shown in FIG. 9, one embodiment of the method 900
may comprise steps: 905, 910, 915, 920, 925, 930, 935, 940, 945,
950, 955, and 960. In step 905, one embodiment of the launcher 100
may be in a stowed configuration (shown in FIG. 10A). Here, the
launcher 100 may comprise forward beam wheels 395, 495 for ease of
transport and may comprise larger components folded for storage.
Specifically, the forward beam portion 420 may be folded onto the
top surface of the aft beam portion 470 via a hinge or pivot,
whereas the pulley drivers 115, 215 may be folded against the
lateral sides of the aft beam portion 470 of the launch rail
105.
In steps 910, 920, and 925, various components of the launcher 100
may be unfolded for launching. Step 910, for instance, may include
unfolding the forward beam portion 420 outwards and away from the
aft beam portion 470. Similarly, in steps 920 and 925, the left
pulley driver 115 and right pulley driver 215 may also be folded
away from the launch rail 105. As recited above, a quick release
pin 430 may be used to lock and secure the unfolded forward beam
portion 420 to the aft beam portion 470, shown in step 915. The
fastening latches, on the other hand, may be used to secure the
left pulley driver 115 and right pulley driver 215 in the launch
configuration, as shown in step 930.
In order to provide an incline for the launcher 100, a user may
lift the distal end of the launcher 100, shown in step 935. The
user may then perform step 940 by installing the leg 106 and a
quick release pin in order to secure the leg 106 onto the launch
rail 105.
In step 945, the user may begin installing the spring compression
cable 805 onto the spring compression cam pulleys 310, 360. This
may help facilitate launching and movement of the slider assemblies
120, 220. The user may also remove the forward beam wheels 395, 495
to provide flight clearance on the launch rail 105 or track 101.
Finally, in steps 955 and 960, the launcher 100 may be ready for
launch after the user deploys the adjustable leveling mounts 192,
292, which may provide additional stability to the launcher
100.
FIGS. 10A to 10C are illustrations of perspective views of one
embodiment of the launcher and shows the launcher in a stowed
configuration, a partially-folded configuration, and a launch
configuration, respectively. Specifically, FIG. 10A shows the
launcher 100 in the stowed configuration; FIG. 10B shows the
launcher 100 in a partially-folded configuration; and FIG. 10C
shows the launcher 100 in a launch configuration.
FIG. 10A depicts the launcher 100 in its stowed configuration or
folded configuration. Here, the launcher 100 may utilize forward
beam wheels 395, 495, which may be larger than the pulley driver
wheels 195, 295. The larger forward beam wheels 395, 495 may
provide the launcher 100 with sufficient ground clearance for ease
of transport, especially when moving the launcher 100 on inclines
and ramps.
FIG. 10A also shows that certain major components of the launcher
100 may be folded for ease of transportation and storage. In
particular, FIG. 10A shows that the launch rail 105 may be folded,
such that the forward beam portion 420 is folded onto the top
surface of the aft beam portion 470 via a hinge. Similarly, the
pulley drivers 115, 215 may also be folded, such that the pulley
drivers 115, 215 are disposed against the lateral sides of the aft
beam portion 470 of the launch rail 105 via hinges. Thus, when the
launch rail 105 and pulley drivers 115, 215 are folded, the
launcher 100 may take only a minimal amount of space in order to
help facilitate storage and improve ease of transportation.
FIG. 10B shows the launcher 100 in a partially-folded
configuration. Here, the launch rail 105 may be in the process of
unfolding when the forward beam portion 420 is opening outwards and
away from the top surface of the aft beam portion 470. FIG. 10B
also shows that the pulley drivers 115, 215 may also be in the
process of unfolding, as the pulley drivers 115, 215 may move away
from the lateral sides of the launch rail 105.
FIG. 10C shows the launcher 100 unfolded and in a launch
configuration. Here, the forward beam wheels 395, 495 may be
removed from the launcher 100 to prevent interference of the
forward beam wheels 395, 495 and unmanned aircraft during launch or
takeoff. A leg 106 may also be attached or coupled to the distal
end of the launch rail 105 to provide an incline for takeoff
purposes.
Importantly, FIG. 10C shows that the launch rail 105 may be fully
unfolded, such that the forward beam portion 420 is fully open
outwards and extended away from the top surface of the aft beam
portion 470. The pulley drivers 115, 215 may also be unfolded and
away from the lateral sides of the launch rail 105, such that the
pulley drivers 115, 215 are substantially aligned with each another
and substantially orthogonal to the launch rail 105. In this launch
configuration, the orientation of the pulley drivers 115, 215 may
be locked into place via toggle clamps in order to secure and
prevent the pulley drivers 115, 215 from folding. Similarly, the
forward beam portion 420 and aft beam portion 470 of the launch
rail 105 may be unfolded and locked into place via a quick release
pin 430.
FIGS. 11A and 11B are illustrations of perspective views of another
embodiment of the launcher that may be attached to a platform of a
vessel such as a ship and show that launcher in a stowed
configuration and launch configuration. Specifically, FIG. 11A
shows the launcher 1000 in the stowed configuration, and FIG. 11B
shows the launcher 1000 in a launch configuration. This embodiment
of the launcher may also be used to reduce the footprint of the
launcher 1000 in order to minimize required space in constrained
areas such as small boats.
As shown in FIGS. 11A and 11B, one embodiment of the launcher 1000
may comprise a launch rail 1050, carriage 1100, and pulley drivers
1150, 2150. Importantly, in this embodiment, the launcher 1000 may
comprise a leg 1060 that is adapted to removeably attach to a
platform of a vessel or ship 2000. The leg 1060 may be angled
upwards, so as to provide a slope or incline for the launcher 1000.
The launcher 1000 may also be connected to deck of the vessel via
tie downs. The forward beam portion 4200 of the launch rail 1050
may also comprise an additional beam 2100 that traverses along the
leg 1060, such that beam 2100 may be substantially aligned with leg
1060. Also, in various embodiments, the launcher 1000 may also lack
adjustable leveling mounts 192, 292, pulley driver wheels, 195,
295, and/or forward beam wheels 395, 495, as these components may
be deemed unnecessary for installation of the launcher 1000 on the
ship or vessel.
FIGS. 12A and 12B are graphs of the carriage velocity and carriage
acceleration as a function of displacement for various embodiments
of the launcher disclosed herein. Specifically, FIG. 12A is a graph
of the carriage velocity, whereas FIG. 12B is a graph of the
carriage acceleration. As shown in FIGS. 12A and 12B, from 0-6 feet
until launch, the carriage velocity may increase in a substantial
near linear manner from 0-80 ft/s. During this time, the carriage
acceleration may also be maintained at a near constant level
between approximately 16-19 g. Thus, the force applied to the
carriage 110 (and therefore the acceleration of the carriage 110)
may be maintained at a constant or nearly constant level until the
unmanned aircraft is launched. One advantage is that any peak force
applied to the unmanned aircraft may be reduced without
significantly increasing the energy required by pulley drivers 115,
215 or the distance required to accelerate the unmanned aircraft to
launch velocity.
The foregoing description of the embodiments of the launcher has
been presented for the purposes of illustration and description.
While multiple embodiments of the launcher are disclosed, other
embodiments will become apparent to those skilled in the art from
the above detailed description. As will be realized, these
embodiments are capable of modifications in various obvious
aspects, all without departing from the spirit and scope of the
present disclosure. Accordingly, the detailed description is to be
regarded as illustrative in nature and not restrictive. Also,
although not explicitly recited, one or more embodiments may be
practiced in combination or conjunction with one another.
Furthermore, the reference or non-reference to a particular
embodiment shall not be interpreted to limit the scope of
protection. It is intended that the scope of protection not be
limited by this detailed description, but by the claims and the
equivalents to the claims that are appended hereto.
Although embodiments of the launcher are described in considerable
detail, including references to certain versions thereof, other
versions are possible such as, for example, orienting and/or
attaching components in different fashion. Therefore, the spirit
and scope of the appended claims should not be limited to the
description of versions included herein.
Except as stated immediately above, nothing which has been stated
or illustrated is intended or should be interpreted to cause a
dedication of any component, step, feature, object, benefit,
advantage, or equivalent to the public, regardless of whether it is
or is not recited in the claims. The scope of protection is limited
solely by the claims that now follow, and that scope is intended to
be broad as is reasonably consistent with the language that is used
in the claims. The scope of protection is also intended to be broad
to encompass all structural and functional equivalents.
* * * * *
References